Parachute-launching device.



Patented Aug: 1.2, 1913.

2 SHEETS-SHEET 1.

anne/Wto@ V ,QG/ini Z :da/(11145 D. W. ADAMS. PARAGHUTB LAUNGHING DEVICE.

APPLICATION FILED 001.6, 1911. 1,069,662.

g a au Wilma/wao D. W. ADAMS. PARAGHUTE LAUNCHING DEVICE.4 APPLIOATION FILED 0011.6, 1911.

1,069,662, Patented Aug. 12, 1913.

2 SHEETS-SHEET 2.

gnou/nto@ (Eni/7461936 BABHEJ W,- Mdl, @E GLENDALE SPRINGS, DIDRTH CABEDLIBIA.

naaacnurnnauncnme ,envien To ali u may concern.' l 4Be Ait known that l, DANIEL W. ADAMS, a citizen of the United vStates, residi at Glendale Springs, in' the county of she and State of North Carolina, have invented new and useful improvements in Parachute- Launchin Devicesgof which the following pas is a speci cation. l

lhis invention relates to apparatus for pro'lecting or launching a parachute toget er with an aviator from an aeroplane while in lli ht at any moment when it is deemed advlsable due toan accident or for other reason. l

'lhe object of my invention is to provide an apparatus which will automatically littl the aviator and the parachute Aand forcibly project them from the aeroplane as soon as the releasing device is operated.

'llt is my purpose to arrange the apparatus in such a manner 'that the aviator 'will he et all times supported 'upon the standard of the parachute, and to place the releasing device wit-hin easy access of his hand so that he may at any moment be carried up out ot the aero lane and be safely'suported and sustaine while'graduall breng t to earth, without being end'angere' 'by tliewrecked or 4uncontrolled machine\ e 'further lrovide orthe gradual initial movement oI the parachute and for an aecelerated velocity as is projected yfrom the aeroplane.

nvention will be comprehended from the' ibllowing descri ion in nconnection with the accompaning raw'rngs illustrating one embodiment t erect, in whichf Figure 1 is aside elevation o vmy launchepparatus, peril vin section; Eig. is a ,sectional elevation o the same taken at right angles to Fig. l; Fig. '3 s a top and sectional view on the line ills-lll of Fi 2;

Figsis an enlarged .detail View or the e vimpressed air tank and the valve operating connections.

Sncoiecticn of Letters Estonia Application also omnes e, reir. soa-ai ne. esame; e

` *19981*- end a handle `33.

Patented Aus i2, 19M,

The arachute and launching mechanism are located in the forward part of the aeroplane in the position usually occupied by the aeronaut. The canopy l, of the parachute is normally folded and is carried by a hollow stem or tube 3,which telesco es over an inner tube 4, extending below the platform of the lower plane and securely fastened by brace rods 6 andlangle pieces 7. The inner tube thus constitutes a rigid standard for the parachute, the inner and outer tubes being preferably accurately fitted with e ground Joint and having a film of oil therebetween. The saddle or seat Si may be fastened to rings or sleeves l0 surrounding the tube '3 and supported upon lu-gs 12. The seat may be swung either in front, in the rear, or at one side of the tube, and locked in osition by means of thumb-screws i4, so tha the aviator may adust his position with relation 'to the steering levers to suit his convenience. AFoot-rests or stirrups i6, may be secured to either side et ythe rod,

which'vv-ill assist the aviator in supporting himself rmly when the parachute is in dight. f

For the purpose or propelling the araehnte upward and forcibly ejecting it from the aeroplane, l utilize the outer and' inner tubes as motor barrel or cylinder and piston eespectively. rihe outer tube or barrel '3 is provided ivith a diaphragm 18; and die' upper end oa the inner tube 4 is closed except for a port 20, the telescoping walls oft the tubes being preferably ground to a close t and made Vari-tight by means of a thin film of oil. 'The lower portion of the inner tube is closed by a diaphragm 22, and ovided with la port Awhich is connected by a small tube Znith a compressed air tank Q5 superted in hangers 26 and constructed to withstand a pressure of over 250 lbs, per

square inch. The delivery 27 from the tank is controlled by a reducing valve of any suitable type, having an openating shaft 28 mounted in bearings and oerryin thepinion 29 and a raduated dial 3G to indicate the position othe valve.

in order that the valve governing the tank .outlet connected with the tubev 24 may be readily controlled by the aviator, l provide "an miuating rod 3l having at its lower end a rack '32 engaging the inion, and at its i he rod may pass through a lhousing orV channel 35 upon one side of the tube, the travel or movement thereof being limited hy the length of the slot`36. A latch 34 may be provided to pre-"1 vent accidental movement of the handle.

The main portioriof the outer tube terlfminates above the platform of the lower plane and is provided upon one sidelwith an extension or depending portion carrying mecha'- regomg endanger hislife, he may instantly start the 1 launching mechanism into operation by liftingthe handle 33,'thereby sliding the rack 32 upward and-.lfrbtatinguthe pinion 29 to open the reducing' valve. slightly and permit a certaingpressure of compressed air to 'pass j from the tank 'into the inner tube 4. The air under pressure passes' from the inner tube through the port 22, which acts as a regulator, and into the small chamber 3*? between vthe topv of the inner tube andthe diaphragm 18 of the outer tube. The pressure against the diaphragm immediately starts the outer tubeupwardly, carryingthe,

parachute, and the aviator, who is securely mounted, being seated upon the saddle with hisfeet resting upon the stirrups 16 and one Ahand gripped upon the vhandle 33, his otherhand or arm being placed `around the tube.

The movable structure will start smoothly,.` and Will accelerate in speed, th'iseffect being increased, if desired by extending the length of the rack 32. After the parts have been .lifted between one and two feet, the lower rack 38 rengages the Apinioxr-ZQ4 to open the tanlrvalve to itsfull extent, throwing the full pressure intothe tubes and projecting l Y the parachute from the' machine with suflicientlvelocity to carry the aviator to a distance' above the-"machine," thus not' only' settingvhi'm'entirel'y free, but in casehe is near v:the ground, lifting him to a height suti'cient to clear' obstructions and enable the parachute to sustain his weight. l A

In order' that the aviator may be easily projected through' the upper plane 40,' in

case the seat is located under the forward portion thereof, the fabric of the plane may. be provided with a thinneror easily tearable' section, as indicated'at 40B.

Owing to the fact that the aviator is seated near thelower end ofthe projected appara-- tus, his weight will cause the center of gravity of the parachute to' be low, and it is evident that it-will right itself very quickly,

Leccese even though it is projected from the aeroplane at an instant when it is carecning at an angle or even pitching toward the earth.

The canopy of -an ordinary parachute will spread as soon as it assumes a substantially vertical descent, and 'if `desired a parachute ofthe self-opening type may be employed, in

which the opening is under control .of the aviator. v

If it is desired to test the operation of the parts before starting, the relief cock 42 may be opened and the valve may then opened to indicate whether it is in workingjo'rder and whether the tank in underproper pressure.

I have described in detail the apparatus illustrated in the accompanying drawings for the purpose of disclosing one embodiment of my invention, but I am aware that many changes may be made in the structure and arrangement of parts without departing from the spirit of my invention.

1. A parachute launching-apparatus comprising a parachute having a tubular stem constituting an outer shell and adapted to serve as a motor cylinder, a source of motivepower, means for connecting said source withthe interior of said tubular stem, and means for controlling the release of said motive-power.

2. A parachute launching-'apparatus prising a parachute having a hollow standard. or stem constituting an outer shell and adapted to serve as a motor cylinder, a source of fluid-pressure, connecting means between said' source and said hollow standard, and valve-mechanism for controlling;

4 the delivery ofsaid fluid-pressure into said standard.

3. A parachute launching-apparatus comfprising a parachute ,having a standard or stem, a source of motive-power, means connecting said source with said standard, man; ually controlled means for causing an initial operation-of said motive-power, and auxilA iary means for causing a thereof. A

4. A parachute launching-apparatus comprising a parachute having'a standard or stem, a source of motive-power, means connecting said sourcewithsaid standard, manually controlled means for causing an linitial further operation tion thereof.

5. Apparatus for launching a lparachute =operation of said motive-power, and auto,- 1

mat-ic means for causing ain lncreased-operaf -1"2'0.

from arraerocraft. comprising a parachute having a hollow stemadapted tQserve as a 'motor cylinder, means 'for Supporting said stem, al sourceof motive-power, means for connecting said source of power with said steunend Vcontrolled means for successively releasing said source of power at different pressures. l

. iso

6. Apparatus for launching a parachute from an aerocraft, comprising a parachute having a hollow stem, an operators support carried thereby, means for supporting said stem, a source of motive-power, means for connecting said source of power with said stern, and means for successively releasing said source of power in increasing amounts.

7. Apparatus for launching a parachute from an aerocraft, comprisingr a parachute having a hollow stem, a hollow7 support adapted to telescope within said stem, a reservoir for compressed motive-fluid connected with said hollow support, and manually controlled means for governing the flow of motive-fluid :from said reservoir.

8. Apparatus for launching a parachute from an aerocraft, comprising a parachute having a hollow stem, a reservoir for compressed motive-fluid connected with said hollow support, a valve for controlling the flow of motive-fluid from said reservoir, manually operated means for opening said valve a predetermined amount, and auxiliary means 'for increasing the valve opening.

9. An aerial navigating device comprising an aerocraft, a parachute having a standard or stem, a support on said stem for holding an operator, a support for said standard carried by said aerocraft, means for projecting said parachute from said aerocraft, and means adjacent said support for controlling the operation of said projecting means.

In testimony whereof I have hereunto set my hand in presence of two subscribing wit-l 35 nesses.

` DANIEL W. ADAMS. lVit-nesses 2 PHILANDER C. JOHNSON, VILLIAM SOHERER. 

